High speed fail safe weapon retarding system

ABSTRACT

An improvement for an aerodynamic missile, such as a torpedo, wherein the missile has a main parachute which is contained by a container at the aft end thereof, the improvement including an initial stabilizing and velocity retarding parachute releasably folded about the container; and means releasably retaining the stabilizing parachute to the container. The container may be constructed of a flexible material such as cloth, and an improved means may be provided for releasing the main parachute from this container.

United States Patent Karp 1 Jan. 30, 1973 541 HIGH SPEED FAIL SAFEWEAPON 2,934,011 4/1960 Fogal ..244/147 x RETARDING Y TEM 3,088,4035/1963 Battling etal... "102 7 3,l45,956 8/1964 Widdows ..244/[47 [75]Inventor: Raymond E. Karp, San Marmo,

Calif- Primary Examiner-Samuel W. Engle [73] Assignee: The United Statesof America as Attorney-R. S. Sclascla and Ervm F. Johnston rNefryesentedby the Secretary of the l ABSTRACT [22] Filed: March 20 1969 Animprovement for an aerodynamic missile, such as a torpedo, wherem themisslle has a mam parachute [21] Appl.No.: 808,725 which is contained bya container at the aft end thereof, the improvement including an initialstabilizing and velocity retarding parachute releasably folded [52]U.S.Cl. ..102/4, l02/7,224;/l4; about the container; and meansreleasably retaining b l t e parachute to the c ai e T e con [58] Fleldof Search ..102/4, 7, 3535.6, tamer y be constructed of a flexiblematerial Such 244/l47'150 as cloth, and an improved means may beprovided for releasing the main parachute from this container. [56]References Cited 8 Claims, 12 Drawing Figures UNITED STATES PATENTS2,581,045 l/l952 Frieder et al. ..244/149 PATENTEU JAN 3 0 I873 SHEET 1OF 5 FIG.

INVENTOR. RAYMOND E. KARP ERVIN F. JOHNSTON ATTORN EY.

Pmmiumaoma 3.713.387

SHEEI 2 {1F 5 PAIENTEU JAN 30 I975 SHEET 3 [IF 5 FIG. 8.

HIGH SPEED FAIL SAFE WEAPON RETARDING SYSTEM The invention describedherein may be manufactured and used by or for the Government of theUnited States of America for governmental purposes without the paymentof any royalties thereon or therefor.

When a weapon, such as a torpedo, is launched form an aircraft at highspeeds, random forces will cause early pitch acceleration and randomtorpedo flight attitudes. To counteract these erratic movements earlytorpedo stabilization is needed and should be initiated at about 0.25second fall position from the aircraft. Most torpedo retarding systemsinclude a main parachute which, if deployed at the 0.25 second fallposition, would cause a serious hazard to the aircraft due to release ofthe parachute container and the sweeping action of the parachute belowthe aircraft. In order to insure the safety of the aircraft parachutedeployment should occur at about 0.9 :02 second after ejection.

Since deployment of the main parachute is hazardous for earlystabilization of the torpedo there is a need for a pre-stabilizer, priorto main parachute deployment, which will operate without any hazard tothe aircraft. It is desirable that the deployment of the stabilizer aswell as the deployment of the main parachute involve a minimum ofdeployed hard components so that maximum safety of the aircraft can beinsured. I have accomplished one of these purposes by providing aninitial stabilizing parachute which is releasably folded about thecontainer of the main parachute at an aft end of the torpedo; andproviding means which releasably retains the stabilizing parachute tothe container. Another purpose of the invention is accomplished byconstructing the main parachute container of a flexible material and byproviding an improved means for releasing the main parachute from thecontainer so that a minimum of hard objects are deployed when the mainparachute is released. In addition to early stabilization of thetorpedo, the stabilizer also retards the velocity prior to mainparachute deployment so that the shock of this latter deployment on thetorpedo is lessened.

An object of the present invention is to provide a retarding system foran aircraft dropped missile, such as a torpedo, wherein deployment ofthe retarding system imposes substantially no hazard to the aircraft.

Another object is to provide a stabilizer for an aircraft droppedtorpedo which will operate to correct early pitch of the torpedo priorto deployment of the main parachute.

Still another object is to provide a stabilizer for a missile which issafe to deploy and which will reduce shock to the missile when a mainparachute is deployed.

A further object is to provide a retarding system for an aircraftdropped torpedo wherein a main parachute is deployed with maximum safetyto the aircraft.

Other objects and many of the attendant advantages of this inventionwill be readily appreciated as it becomes better understood by referenceto the description and accompanying drawings which follow.

FIGS. I through 5 illustrate side views of a torpedo and various stagesof deployment of a retarding system subsequent to drop from the bombayof an aircraft;

FIGS. 6 and 7 illustrate the initial two stages of operation of thepresent torpedo retarding system in cooperation'with a missile airframe.Subsequent stages of this embodiment are similar to FIGS. 3, 4, and 5;

FIG. 8 is a sideview of the present torpedo retarding system withportions cut away to show details thereof;

FIG. 9 is a view taken along plane IX-IX of FIG. 8;

FIG. 10 illustrates an enlarged top view of the strap release assemblyat the top of FIG. 9;

FIG. 11 is a view taken along plane XI-XI of FIG. 10; and

FIG. 12 is a longitudinal cross-sectional view through a dual pinretractor for the torpedo retarding system.

Referring now to the drawings wherein like reference numerals designatelike or similar parts throughout the several views there is shown inFIG. 1 a missile, such as a torpedo 20, which is generally designated at22.

The retarding system 22 includes a small stabilizer parachute 24 whichis shown deployed in FIG. 2. As shown in FIG. 2 the shroud lines 24a ofthe stabilizer parachute are connected to a container 26 for a mainparachute. The main parachute 28 is shown deployed in FIG. 3, andlocated aft thereof is a deployment bag 30 which previously containedthe main parachute. Connected to the deployment bag 30 and the mainparachute 28 by a break line 32 is the container 26 which previouslycontained the deployment bag 30 and the main parachute 28.

The details of the various retarding system components in theirunreleased conditions are illustrated in FIG. 8. The retarding system 22is releasably connected to the tail end 34 of the torpedo by a releasemechanism 36 which includes a ring assembly 38. The release mechanism 36and a portion of the ring assembly 38 is shown in my previous US. Pat.No. 3,153,395 entitled Parachute Release Mechanism which is incorporatedby reference herein. As will become fully apparent hereinafter the ringassembly 38 serves the function of a portion of a means for retainingboth the stabilizer parachute 24 and the container 26 for the mainparachute 28.

In order to protect the aircraft upon release of the container 26 I havefound it desirable to construct the container of a flexible material,such as a fabric of cloth. As shown at the top of FIG. 8, thisconstruction has the advantage of enabling an easy connection of thestabilizer shroud lines 24 to the container 26 by stitching at 40. Theother end of the stabilizer shroud lines 240 are stitched to thestabilizer canopy 24 at 42. The stabilizer canopy 24 is folded over asmany times as necessary about the container 26 with an exterior portionappearing as shown in the top portion of FIG.

As shown in FIG. 8, the container 26 extends forward over the ringassembly 38 for a releasable connection thereto. This paragraphdescribes the means for deploying the main parachute 28 and the bag 30from the container 26. The ring assembly 38 may be provided with aradially extending annular ledge 44, and a forward edge 46 of thecontainer 26 may be folded over this transverse ledge 44. As illustratedin FIGS. 8 and 9, the forward edge 46 of the container 26 may beprovided with a series of eyelets 48 and this eyelet area may bestrengthened by folding the container material back and stitching it onitself. In order to draw the container 26 into a tight unreleasedcondition about the ring 38 lacing 50 is laced through the eyelets 48and is held in a taut unreleased condition by a pin 52 of a pinretractor 54 which will be described more fully hereinbelow.

I have found it desirable to use a pair of cords for the lacing 50 whichare tied together at 56 and are looped in an adjacent alignedrelationship for retention purposes about the retractable pin 52. inorder to protect the aircraft at the time of deployment of thestabilizer parachute 24 I have found it desirable to releasably foldthis parachute about the container 26, as stated hereinabove, andprovide a means for releasably retaining the stabilizer parachute 24 tothe container. An exemplary releasable retaining means may include thering 38 being provided with an aftermost annular lip 58 over which mayextend the canopy of the stabilizer parachute 24 in a folded condition.A series of straps 60 may be stitched to the exterior portion of thestabilizer canopy 24 in its folded condition about the container 26 andthe forward ends of these straps may be provided with transverselygrooved clasps 62 which extend over and forward of the lip 58 of thering assembly. A releasable band 64 may be disposed about these strapsin the annular grooves of the clamps 62 and may be located forward ofthe lip 58 for retaining these straps 60 and the stabilizer parachute 24to the container 26. If desired, the band 64 may be connected by a rivet65 to one of the clasps 62 (see bottom of FIG. 8).

An exemplary means for retaining the band is shown in FIGS. and 11wherein the left end of the band 64 is pivotally connected to a block 66by a pin 68. The block 66 is connected to another block 70 by aturnbuckle 72 and the block 70 is in turn pivoted to opposite sides of aU shaped element 74 by a pin 76. Another block 78 is also pivoted withinthe U shaped element 74 by a pin 80 and this block is provided with abottom hemispherical cavity 82 which is positioned opposite ahemispherical cavity 84 in the u shaped element 74 when the block 78 isin a closed position, as shown in FIG. 10. The right end of the band 64extends between the block 78 and the bottom of the U shaped element 74and has a small aperture in the area of the hemispherical cavities 82and 84 to enable placement of a ball 86 therein for retaining the bandwhen the block 78 is in the closed position. To retain the block 78 inthe closed position, as shown in FIG. 10, a retractable pin 88 from thepin retractor 74 may extend through both the U shaped element 74 and theblock 78. When this pin 88 is retracted the block 78 is allowed to pivotupwardly around the pin 80 to release the ball 86 and the band 64. Therelease of the band 64 in turn releases the stabilizer parachute 24 fromthe container 26. To provide a bearing surface against the torpedo aband 89 may be connected to the bottom of the U shaped element 74 by anysuitable means such as welding.

As shown in FIGS. 8 and 12 the pin retractor assembly 54 for retractingpins 88 and 52 may be mounted to the ring assembly 38 by bolts 90, oneof which is shown in FIG. 12. The pin retractor 54 includes a pair ofsears 92 and 94 which are pulled by arming wires at the time the torpedois dropped from the aircraft. As shown in FIG. 1, the arming wires maybe fixably connected to the bombay of the aircraft at 96. The retractor54 is constructed so that when the sears 92 and 94 are pulled the pin 88is retracted almost immediately and the pin 52 is retracted after adesired delay. When the sear 92 is pulled a ball 98 releases apiston-type firing pin 100 from a cylinder 102 so that the pin 100 isdriven to the right by a compression spring 104 to tire an igniter 106which in turn ignites an explosive charge 108. The explosive charge 108then generates a gas under pressure which travels through a passageway110 of a cylinder 112 to the right end of a piston 114 which isconnected to the left end of the retractable pin 88. The piston 114 thenmoves to the left within the cylinder 112 so as to retract the pin 88and release the band 64. This then immediately releases the stabilizerparachute 24. A vent 116 to the atmosphere is provided in the cylinder112. An identical construction may be provided in the bottom portion ofthe retractor 54 for retracting the pin 52 except a charge 118 isprovided with a delay explosive mix so that the pin 52 will not beretracted until a redetermined period of time after the pulling of thesear 94.

Returning now to FIG. 8, the main parachute has shroud lines 28a (one ofwhich is shown in the bottom portion of FIG. 8) which are connected tothe ring assembly 38 by transverse blocks 120. The main parachute 28 andthe major portions of the shroud lines 28a are contained within thedeployment bag 30. The deployment bag 30 is open at its after end andhas a longitudinal door. These details can be seen in FIG. 3. As shownin FIG. 8 the edges of the door may be provided with eyelets 122 throughwhich there is releasably looped a cord 124. The end of the looped cord124 is locked by a line 126 which is secured to the main parachuteshroud 28a. When the deployment bag 30 is deployed the after movement ofthe bag will pull the free end of the line 126 from the end loop of thecord 124 so that the cord 124 will unravel from the eyelets 122 to openthe door of the deployment bag and deploy the main parachute 28.

In order to actuate the release means 36 so as to release the ringassembly 38 and the entire retarding system 22 from the tail end of thetorpedo 20 a line is connected between the main parachute shroud 28a andan actuating pin 130 of the release mechanism 36. The shroud 28a istemporarily shortened by a rubber band 132 so as to insure pulling ofthe pin 130 at approximately the time of full extension of the shroudlines of the main parachute 28. This occurs in the stage illustrated inFIG. 3.

In the operation of the present invention, for a torpedo launched froman aircraft bombay (see FIG. 1), a pair of bomb rack hooks 134, whichare connected to a pair of torpedo suspension bands 136, areelectrically opened by an aircraft bomb release system (not shown). Thetorpedo is then released from the aircraft bombay and the drop of thetorpedo causes the arming wires to pull sears 92 and 94. The pulling ofsear 92 causes the pin 88 to be retracted so as to release thesuspension band 64 and the stabilizing parachute 24. This stage isillustrated in FIG. 2 wherein the stabilizing parachute 24 stabilizesthe torpedo early in its flight so as to prevent the torpedo frompitching into a position in contact with the aircraft. The stabilizerparachute 24 also retards the acceleration of the torpedo and after apredetermined period, about 0.9 10.2 second after ejection, the pin 52is retracted which causes the container 26 to be released and the mainparachute 28 to be deployed, as shown in FIG. 3. Since there aresubstantially no hard components involved in the release of thestabilizing parachute 24 or the main parachute 28 there is no hazard ofany flying debris to the aircraft. In about the position of the mainparachute 28 in FIG. 3, a lanyard 138, which is connected between themain parachute shrouds 28 and the suspension bands 136, causes a releaseof the suspension bands 136. Also, at

this time one of the main parachute shrouds 28a pulls pin 130 of therelease mechanism 136 which activates a G sensor (not shown) within therelease mechanism 36.

Upon impact of the torpedo with the water, as shown in' FIG. 5, the Gsensor is activated and the release mechanism 36 causes the entireretarding system 22 including the ring 38 to be separated from the tailend 34 of the torpedo. The torpedo is now operational within the water.

Another embodiment of the present invention is illustrated in FIGS. 6and 7. This torpedo is normally fired from a shipboard location with amissile airframe assembly 140. At a predetermined time the airframe 140pivots to an open position causing attached arming wires to pull thesears 92 and 94. As shown in FIG. 7, the stabilizing parachute 24 isthen deployed in the same manner as shown in FIG. 2. The torpedo isearly stabilized without any fouling with the airframe assembly 140. Thesubsequent stages of the torpedo are substantially identical to thestages illustrated in FIGS. 3, 4, and 5.

Other objects and many of the attendant advantages of this inventionwill be readily appreciated as it becomes better understood by referenceto the description and accompanying drawings which follow.

Iclaim:

1. In an aerodynamic missile having a main parachute which is containedby a container at the aft end of the missile, a means for releasing themain parachute from the container comprising:

a ring connected to the aft end of the missile and having a radiallyextending annular ledge;

said container being folded over the transverse ledge;

lacing extending through the folded over portion of the container fordrawing the container into a tight unreleased condition about the ring;and

means carried by the ring for releasing the lacing so as to in turndeploy the main parachute from the container.

2. The combination of claim 1 wherein:

the lacing is a double cord which ends in a pair of aligned loops; and

the lacing releasing means includes a retractable pin extending throughthe aligned loops.

3. In an aerodynamic missile having a main parachute which is containedby a container at the aft end of the missile, the improvementcomprising:

an initial stabilizing and velocity retarding parachute releasablyfolded about said container;

means releasably retaining the stabilizing parachute to said container,the retainer means including:

a ring connected to the aft end of the missile and having an aftermostoutwardly extending annular lip;

a series of straps connected to the canopy of the stabilizing parachuteand extending over and forward of the lip of said ring;

a releasable band disposed about the straps forward of the lip forretaining the straps and the stabilizing parachute to the container; and

meanscarried by the ring for releasing the band so that the stabilizingparachute can be released from the container;

the container being constructed of a flexible material; and

the stabilizing parachute having shrouds which are stitched to saidcontainer.

4. The combination of claim 3 including:

a means for releasing the main parachute from the container, said meanscomprising:

said ring having a transverse annular ledge;

said container being folded over the transverse ledge;

lacing extending through the folded-over portion of the container fordrawing the container into a tight unreleased condition about the ring;and

means carried by the ring for releasing the lacing so as to in turndeploy the main parachute from the container.

5. The combination of claim 4 including:

the lacing being a double cord which ends in a pair of aligned loops;and

the lacing releasing means being a retractable pin extending through thealigned loops.

6. The combination as claimed in claim 5 including:

the main parachute having shrouds which are connected to said ring;

a deployment bag with the main parachute disposed therein, saiddeployment bag having eyelets;

a cord releasably looped through the eyelets of the deployment bag; and

a lock line connected to a shroud line of the main parachute andextending through a loop of the looped cord for locking the deploymentbag until released by said container.

7. In an aerodynamic missile having a main parachute which is containedby a container at the aft end of the missile, the improvementcomprising:

an initial stabilizing and velocity retarding parachute releasablyfolded about said container;

means releasably retaining the stabilizing parachute to said container;

the container being constructed of a flexible materithe stabilizingparachutehaving shrouds which are stitched to said container; and

means for deploying the main parachute from the container, said meanscomprising:

a ring connected to the aft end of the missile and having a radiallyextending annular ledge;

said container being folded over the transverse ledge;

lacing extending through the folded-over portion of the container fordrawing the container into a tight unreleased condition about the ring;and

means carried by the ring for releasing the lacing so as to in turndeploy the main parachute from the container.

8. The combination as claimed in claim 7 wherein:

the lacing is a double cord which ends in a pair of aligned loops; and

the lacing releasing means includes a retractable pin extending throughthe aligned loops.

1. In an aerodynamic missile having a main parachute which is contained by a container at the aft end of the missile, a means for releasing the main parachute from the container comprising: a ring connected to the aft end of the missile and having a radially extending annular ledge; said container being folded over the transverse ledge; lacing extending through the folded over portion of the container for drawing the container into a tight unreleased condition about the ring; and means carried by the ring for releasing the lacing so as to in turn deploy the main parachute from the container.
 1. In an aerodynamic missile having a main parachute which is contained by a container at the aft end of the missile, a means for releasing the main parachute from the container comprising: a ring connected to the aft end of the missile and having a radially extending annular ledge; said container being folded over the transverse ledge; lacing extending through the folded over portion of the container for drawing the container into a tight unreleased condition about the ring; and means carried by the ring for releasing the lacing so as to in turn deploy the main parachute from the container.
 2. The combination of claim 1 wherein: the lacing is a double cord which ends in a pair of aligned loops; and the lacing releasing means includes a retractable pin extending through the aligned loops.
 3. In an aerodynamic missile having a main parachute which is contained by a container at the aft end of the missile, the improvement comprising: an initial stabilizing and velocity retarding parachute releasably folded about said container; means releasably retaining the stabilizing parachute to said container, the retainer means including: a ring connected to the aft end of the missile and having an aftermost outwardly extending annular lip; a series of straps connected to the canopy of the stabilizing parachute and extending over and forward of the lip of said ring; a releasable band disposed about the straps forward of the lip for retaining the straps and the stabilizing parachute to the container; and means carried by the ring for releasing the band so that the stabilizing parachute can be released from the container; the container being constructed of a flexible material; and the stabilizing parachute having shrouds which are stitched to said container.
 4. The combination of claim 3 including: a means for releasing the main parachute from the container, said means comprising: said ring having a transverse annular ledge; said container being folded over the transverse ledge; lacing extending through the folded-over portion of the container for drawing the container into a tight unreleased condition about the ring; and means carried by the ring for releasing the lacing so as to in turn deploy the main parachute from the container.
 5. The combination of claim 4 including: the lacing being a double cord which ends in a pair of aligned loops; and the lacing releasing means being a retractable pin extending through the aligned loops.
 6. The combination as claimed in claim 5 including: the main parachute having shrouds which are connected to said ring; a deployment bag with the main parachute disposed therein, said deployment bag having eyelets; a cord releasably looped through the eyelets of the deployment bag; and a lock line connected to a shroud line of the main parachute and extending through a loop of the looped cord for locking the deployment bag until released by said container.
 7. In an aerodynamic missile having a main parachute which is contained by a container at the aft end of the missile, the improvement comprising: an initial stabilizing and velocity retarding parachute releasably folded about said container; means releasably retaining the stabilizing parachute to said container; the container being constructed of a flexible material; the stabilizing parachute having shrouds which are stitched to said container; and means for deploying the main pArachute from the container, said means comprising: a ring connected to the aft end of the missile and having a radially extending annular ledge; said container being folded over the transverse ledge; lacing extending through the folded-over portion of the container for drawing the container into a tight unreleased condition about the ring; and means carried by the ring for releasing the lacing so as to in turn deploy the main parachute from the container. 